US4047464A - Umbilical cord breaker - Google Patents

Umbilical cord breaker Download PDF

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Publication number
US4047464A
US4047464A US05/653,325 US65332576A US4047464A US 4047464 A US4047464 A US 4047464A US 65332576 A US65332576 A US 65332576A US 4047464 A US4047464 A US 4047464A
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US
United States
Prior art keywords
missile
conductors
insert
continuous
container
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired - Lifetime
Application number
US05/653,325
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English (en)
Inventor
Lars Evert Fredriksson
Gunnar Jacobson
Olof Bertil Olsson
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Saab Bofors AB
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Bofors AB
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Publication date
Application filed by Bofors AB filed Critical Bofors AB
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Publication of US4047464A publication Critical patent/US4047464A/en
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    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01B—CABLES; CONDUCTORS; INSULATORS; SELECTION OF MATERIALS FOR THEIR CONDUCTIVE, INSULATING OR DIELECTRIC PROPERTIES
    • H01B17/00—Insulators or insulating bodies characterised by their form
    • H01B17/26—Lead-in insulators; Lead-through insulators
    • H01B17/30—Sealing
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41F—APPARATUS FOR LAUNCHING PROJECTILES OR MISSILES FROM BARRELS, e.g. CANNONS; LAUNCHERS FOR ROCKETS OR TORPEDOES; HARPOON GUNS
    • F41F3/00—Rocket or torpedo launchers
    • F41F3/04—Rocket or torpedo launchers for rockets
    • F41F3/055—Umbilical connecting means

Definitions

  • the missile is usually kept in a missile container, which also serves as a launching tube. While the missile is in the missile container, it is connected by an electric cable with the missile container and a control unit for the missile.
  • This cable transmits electric signals to the missile while the missile is in storage to test its various functions. When the missile is used in field service, this cable transmits the necessary starting signals to the missle.
  • this cable connection must be broken in such a way that, after said breaking, no remnants of the cable will be dragged along by the missile. Because of the high velocity of the missile, its aerodynamic properties are seriously affected if the contact device in the missile has an influence on the air flow around the missile, which is smooth in other respects.
  • the extractable contact device usually consists of a connection by contacts made between the missile and the missile container.
  • the contact device is placed at the rear of the missile in such a way that male and female contacts are located axially parallel to the axis of the missile.
  • the male contact will automatically be pulled out of the female contact, thereby breaking the connection between the missile and the missile container.
  • Such contact devices are not suitable for use in missiles equipped with a separate booster motor which can be jettisoned in flight. If such a contact device is used, in this case, a further contact connection must be provided between the booster motor and the rear surface of the missile. The further contact is broken when the booster motor is jettisonal.
  • the guillotine devices consist essentially of two nonconductive plates which can slide in relation to each other, and are provided with through holes at right angles to the direction in which they slide.
  • the cable between the missile and the missile container can be passed through one such hole, or specific electrical conductors in the cable can be passed through separate holes.
  • the device comprises an insert made of electrically non-conducted material located in the wall of the missile.
  • the insert is provided with a number of through holes to accommodate the various conductors located in the electric cable connection.
  • the insert in the wall of the missile is arranged in such a way that its outer surface constitutes a part of the envelope surface of the missile and fits flush with the surface.
  • the electric cable is anchored in securing devices in both the missile and the missile container so that when the missile starts the cable will be straight and nearly parallel to the longitudinal axis of the missile, and will not be bent at any place other than just over the outer edge of the through holes. The electrical conductors of the cable will then be broken off at the envelope surface of the missile.
  • FIG. 1 shows schematically the electric cable between a missile and its missile container.
  • FIG. 2 shows a detailed view of the insert, or umbilical cord breaker, which effects the breaking of the electrical conductors at the place desired.
  • FIG. 3 shows a view of the electrical conductors of the cable just before breaking.
  • a missile weapon typically comprises three parts: a guided projectile, such as the missile 1; a storage container 2 for the missile, which also serves as a launching tube; and a missile control unit 3.
  • a guided projectile such as the missile 1
  • a storage container 2 for the missile which also serves as a launching tube
  • a missile control unit 3 Before launch, the missile 1 is placed in the missile container 2, and is secured mechanically by means of a missle lock (not shown).
  • Missile 1 is connected with missile container 2 by means of an electric cable 4, a so-called umbilical cord which extends across an open annulus separating missile 1 from container 2, as shown. Through cable 4, electric signals may be sent to missile 1 when it is in storage to test its function.
  • cable 4 transmits the required starting signals to missile 1 from the control unit 3.
  • missile 1 starts, the cable 4 is broken, and missile 1 is guided toward its target automatically or with the aid of an operator.
  • Cable 4 comprises a group of separate electrical conductors. The number of conductors can vary, depending on the number of control signals to be transmitted to missile 1. In FIG. 1, a cable comprising five separate electrical conductors has been chosen as an example.
  • the conductors pass through an insert 5, the so-called umbilical cord breaker, which constitutes a part of the envelope surface of missile 1, and is placed in the vicinity of the electronic part of the missile, which has been indicated schematically by the block 6.
  • the conductors pass through an electric disturbance filter 7 which is joined to insert 5 by a screen wall 37. Filter 7 screens the missile from external high frequency disturbances.
  • a terminal bar 8 joins the conductors to electronic part 6.
  • the screen wall 37 is connected with the casing of the missile, which is also made of an electrically conductive material.
  • the conductors are secured mechanically to insert 5 by means such as a body 9 of thermosetting resin, into which the individual conductors have been cast. In order to prevent the conductors from sliding in the material of block 9, they can be made with an enlarged portion such as a knot, loop or the like 10 (see FIG. 2) cast in the thermosetting resin.
  • Cable 4 is led out through a hole 11 in missile container 2 to a junction box 12 on the outer wall of the missile container.
  • Junction box 12 encloses a securing device 13 which anchors cable 4 to the wall of the missile container, and a removable contact device in the form of a male contact 14 connected with the cable 4 and a female contact 15 connected to control unit 3 by a securing device 36 and a cable 16.
  • FIG. 2 shows in more detail the appearance of the so-called umbilical cord breaker 5, which comprises a body made of electrically non-conductive material.
  • Breaker 5 is screwed into place by means of screws 17, 18 passing through the outer casing 19 of the missile so that it constitutes a part of the envelope surface of the missile.
  • the breaker 5 also is provided with through holes 20 for the individual conductors. These holes may be drilled at right angles to the envelope surface or at an oblique angle. In the latter case, the outlet opening of the oblique hole is located farther towards the front of the missile than the opening of the hole at the inside of breaker 5, as illustrated. The center line through the hole will thereby form an angle ⁇ to the envelope surface of the missle which is less than 90°.
  • FIG. 1 shows in more detail the appearance of the so-called umbilical cord breaker 5, which comprises a body made of electrically non-conductive material.
  • Breaker 5 is screwed into place by means of screws 17, 18 passing through the outer casing 19 of the missile so
  • the arrow 22 indicates the direction of travel of the missile. It is essential that the material of breaker 5 is not only electrically non-conductive, but also is hard. Moreover, it is essential that the outlet openings 21 have sharp edges 23. In order to optimize the cutting edge effect, that is, to ensure that the edge at the outlet opening is sufficiently sharp to achieve the cutting of the conductors, breaker 5 can be provided with metal inserts 24 surrounding openings 21, each metal insert being electrically insulated from the other metal inserts. In FIG. 2, one of the holes is shown with such a metal insert 24.
  • the umbilical cord breaker constitutes a part of the envelope surface of the missile, and it is essential that its outer surface 25 fits in well with the outer surface of the missile.
  • the purpose of the umbilical cord breaker 5 is to insure that when the missile starts, the conductors of cable 4 will be broken immediately at the envelope surface. Due to the high velocities which missiles of this kind attain in flight, any unevenness on the envelope surface of the missile can cause very great disturbances of the aerodynamics around the missile body. It has been shown that cable stubs protruding only a few millimeters can have a disturbing effect. When the conductors are broken off, it may happen that the actual electrical conductor is broken off at one place and the insulation at another place.
  • thermosetting resin 26 fits well into the outer surface of the missile.
  • FIG. 3 shows an alternative embodiment, in which the hard material of breaker 5 extends all the way out to and is flush with the outer surface of the missile. Breaker 5 is moreover provided with flanges 27, 28 extending into the internal parts of the missile, which facilitates the casting of the cables in the thermosetting resin 9.
  • the umbilical cord breaker functions in the following way.
  • cable 4 will be stretched out between the two securing devices, the device 13 in the missle container and the device 9 in the missle. It is then essential that the transmission of the strictly tensile stress which arises in the cable between the two securing devices takes place in such a way that the electrical conductors in the cable are not subjected to anything but strictly a tensile stress at any point other than just at the edge of the outlet hole 21. That is, to the greatest possible extent cable 4 is straight when it is stretched out, and is not bent at any point other than just over the cutting edge 23.
  • the conductors assume a position according to FIG.
  • the conductors will thereby reach the breaking stress only at point 31, which will be the point where the cable connection breaks and is torn off.
  • point 31 which will be the point where the cable connection breaks and is torn off.
  • a cable with few conductors than a cable with many conductors. It is moreover more advantageous to have a brittle electrical conductor than a tough conductor.
  • Hard drawn copper for instance, is more appropriate than annealed copper.
  • the cable insulation should be brittle-hard, rather than soft.
  • the angle ⁇ at which the cable leaves the envelope surface of the missile when stretched out in connection with the start of the missile should be as little as possible, at the same time as the angle ⁇ , i.e. the angle between the hole 20 and the longitudinal axis of the missile should also be as small as possible. This involves that the efficient cutting edge angle chosen ⁇ + ⁇ should be as small as possible.
  • the conductors are arranged in such a way that when the missile starts, all of the wires are not stretched out simultaneously. It is advisable to have the individual conductors of different lengths, so that the stretching out takes place successively.
  • it can, for instance, be the conductor 32 which is first stretched out so that it breaks.
  • the conductor 33 is stretched out, and when this has been broken the conductor 34 is stretched out, thereafter the conductor 35 and so forth.
  • the conductors are therefore broken off one at a time, about like when a paper is torn.

Landscapes

  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Cable Accessories (AREA)
  • Electrical Discharge Machining, Electrochemical Machining, And Combined Machining (AREA)
  • Spinning Or Twisting Of Yarns (AREA)
  • Numerical Control (AREA)
  • Communication Cables (AREA)
  • Insulating Bodies (AREA)
US05/653,325 1975-02-19 1976-01-29 Umbilical cord breaker Expired - Lifetime US4047464A (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
SE7501822A SE397407B (sv) 1975-02-19 1975-02-19 Avrivningskontaktdon
SW7501822 1975-02-19

Publications (1)

Publication Number Publication Date
US4047464A true US4047464A (en) 1977-09-13

Family

ID=20323721

Family Applications (1)

Application Number Title Priority Date Filing Date
US05/653,325 Expired - Lifetime US4047464A (en) 1975-02-19 1976-01-29 Umbilical cord breaker

Country Status (10)

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US (1) US4047464A (GUID-C5D7CC26-194C-43D0-91A1-9AE8C70A9BFF.html)
JP (1) JPS51107700A (GUID-C5D7CC26-194C-43D0-91A1-9AE8C70A9BFF.html)
CH (1) CH606969A5 (GUID-C5D7CC26-194C-43D0-91A1-9AE8C70A9BFF.html)
DE (1) DE2606480A1 (GUID-C5D7CC26-194C-43D0-91A1-9AE8C70A9BFF.html)
FR (1) FR2301802A1 (GUID-C5D7CC26-194C-43D0-91A1-9AE8C70A9BFF.html)
GB (1) GB1533273A (GUID-C5D7CC26-194C-43D0-91A1-9AE8C70A9BFF.html)
IT (1) IT1053940B (GUID-C5D7CC26-194C-43D0-91A1-9AE8C70A9BFF.html)
NL (1) NL7601119A (GUID-C5D7CC26-194C-43D0-91A1-9AE8C70A9BFF.html)
NO (1) NO138816C (GUID-C5D7CC26-194C-43D0-91A1-9AE8C70A9BFF.html)
SE (1) SE397407B (GUID-C5D7CC26-194C-43D0-91A1-9AE8C70A9BFF.html)

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4099038A (en) * 1976-12-22 1978-07-04 The United States Of America As Represented By The Secretary Of The Navy Separable electrical flexible cable assembly for moving stores such as missiles
US4184731A (en) * 1977-04-13 1980-01-22 Messerschmitt-Bolkow-Blohm Gmbh Electrical connector for use inside a tube such as an ejector tube
US5551368A (en) * 1994-01-10 1996-09-03 L'etat Francais, Represente Par Le Delegue Ministeriel Pour L'armement Container for launching a lightweight torpedo from a surface craft
FR2737918A1 (fr) * 1995-08-16 1997-02-21 Whitaker Corp Cordon ombilical pour dispositif de lancement de projectile
US6146188A (en) * 1999-11-02 2000-11-14 Amphenol Corporation High density shear connector
WO2004018956A1 (fr) * 2002-08-21 2004-03-04 Forges De Zeebrugge S.A Connectique entre un lanceur militaire et des munitions resistant a l'encrassage
US20050134513A1 (en) * 2003-12-19 2005-06-23 Lockheed Martin Corporation Combination conductor-antenna
WO2014120283A1 (en) * 2012-11-13 2014-08-07 Raytheon Company Umbilical cable disconnect
CN109737828A (zh) * 2019-01-14 2019-05-10 北京星际荣耀空间科技有限公司 一种火箭起飞状态判别方法，系统及设备
EP3491423A4 (en) * 2016-07-29 2020-04-08 Saint-Gobain Ceramics&Plastics, Inc. GASKET FOR ELECTRICAL CONNECTION

Families Citing this family (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3706819A1 (de) * 1987-03-03 1988-09-15 Diehl Gmbh & Co Submunition mit zuendeinrichtung
RU2167384C1 (ru) * 2000-02-10 2001-05-20 Новосибирский завод искусственного волокна Ракета
RU2233420C2 (ru) * 2002-08-20 2004-07-27 Государственное унитарное предприятие "Конструкторское бюро приборостроения" Способ обеспечения электропитанием бортовой аппаратуры управляемой ракеты и управляемая ракета в транспортно-пусковом контейнере для его осуществления
RU2246093C1 (ru) * 2003-07-22 2005-02-10 Государственное унитарное предприятие "Конструкторское бюро приборостроения" Двухступенчатая бикалиберная ракета
RU2247919C1 (ru) * 2003-07-22 2005-03-10 Государственное унитарное предприятие "Конструкторское бюро приборостроения" Ракета в пусковом контейнере
RU2247920C1 (ru) * 2003-07-22 2005-03-10 Государственное унитарное предприятие "Конструкторское бюро приборостроения" Ракета
RU2367894C1 (ru) * 2008-02-11 2009-09-20 Государственное унитарное предприятие "Конструкторское бюро приборостроения" Способ управления стартом ракеты и ракетный комплекс
RU2367895C1 (ru) * 2008-04-23 2009-09-20 Государственное унитарное предприятие "Конструкторское бюро приборостроения" Способ монтажа ракеты

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2951421A (en) * 1958-01-28 1960-09-06 Gen Electric Frangible connector
US3072021A (en) * 1961-02-23 1963-01-08 Lewis J Marcon Missile umbilical assembly
US3122403A (en) * 1961-12-18 1964-02-25 Gen Dynamics Corp Electrical disconnect
US3136842A (en) * 1961-06-12 1964-06-09 James M Perkins Expendable frangible connector
US3611274A (en) * 1970-02-28 1971-10-05 Nasa Breakaway connector

Family Cites Families (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3839596A (en) * 1973-05-07 1974-10-01 Amp Inc Flexible airtight stranded wire

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2951421A (en) * 1958-01-28 1960-09-06 Gen Electric Frangible connector
US3072021A (en) * 1961-02-23 1963-01-08 Lewis J Marcon Missile umbilical assembly
US3136842A (en) * 1961-06-12 1964-06-09 James M Perkins Expendable frangible connector
US3122403A (en) * 1961-12-18 1964-02-25 Gen Dynamics Corp Electrical disconnect
US3611274A (en) * 1970-02-28 1971-10-05 Nasa Breakaway connector

Cited By (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4099038A (en) * 1976-12-22 1978-07-04 The United States Of America As Represented By The Secretary Of The Navy Separable electrical flexible cable assembly for moving stores such as missiles
US4184731A (en) * 1977-04-13 1980-01-22 Messerschmitt-Bolkow-Blohm Gmbh Electrical connector for use inside a tube such as an ejector tube
US5551368A (en) * 1994-01-10 1996-09-03 L'etat Francais, Represente Par Le Delegue Ministeriel Pour L'armement Container for launching a lightweight torpedo from a surface craft
FR2737918A1 (fr) * 1995-08-16 1997-02-21 Whitaker Corp Cordon ombilical pour dispositif de lancement de projectile
US5710388A (en) * 1995-08-16 1998-01-20 The Whitaker Corporation Umbilical cord for projectile launching device
US6146188A (en) * 1999-11-02 2000-11-14 Amphenol Corporation High density shear connector
WO2004018956A1 (fr) * 2002-08-21 2004-03-04 Forges De Zeebrugge S.A Connectique entre un lanceur militaire et des munitions resistant a l'encrassage
BE1015204A3 (fr) * 2002-08-21 2004-11-09 Zeebrugge Forges Sa Connectique entre un lanceur militaire et des munitions resistant a l'encrassage.
US20050134513A1 (en) * 2003-12-19 2005-06-23 Lockheed Martin Corporation Combination conductor-antenna
US20070238412A1 (en) * 2003-12-19 2007-10-11 Lockheed Martin Corporation Combination conductor-antenna
US7786416B2 (en) 2003-12-19 2010-08-31 Lockheed Martin Corporation Combination conductor-antenna
US8618996B2 (en) 2003-12-19 2013-12-31 Lockheed Martin Corporation Combination conductor-antenna
WO2014120283A1 (en) * 2012-11-13 2014-08-07 Raytheon Company Umbilical cable disconnect
US20150153135A1 (en) * 2012-11-13 2015-06-04 Raytheon Company Umbilical cable disconnect
US9074842B2 (en) * 2012-11-13 2015-07-07 Raytheon Company Umbilical cable disconnect
EP3491423A4 (en) * 2016-07-29 2020-04-08 Saint-Gobain Ceramics&Plastics, Inc. GASKET FOR ELECTRICAL CONNECTION
CN109737828A (zh) * 2019-01-14 2019-05-10 北京星际荣耀空间科技有限公司 一种火箭起飞状态判别方法，系统及设备

Also Published As

Publication number Publication date
SE7501822L (sv) 1976-08-20
NL7601119A (nl) 1976-08-23
DE2606480A1 (de) 1976-08-26
NO760477L (GUID-C5D7CC26-194C-43D0-91A1-9AE8C70A9BFF.html) 1976-08-20
IT1053940B (it) 1981-10-10
FR2301802A1 (fr) 1976-09-17
SE397407B (sv) 1977-10-31
NO138816B (no) 1978-08-07
JPS51107700A (GUID-C5D7CC26-194C-43D0-91A1-9AE8C70A9BFF.html) 1976-09-24
GB1533273A (en) 1978-11-22
NO138816C (no) 1978-11-15
CH606969A5 (GUID-C5D7CC26-194C-43D0-91A1-9AE8C70A9BFF.html) 1978-11-30

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